CN106932187A - A kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig and test method - Google Patents
A kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig and test method Download PDFInfo
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- CN106932187A CN106932187A CN201710190128.2A CN201710190128A CN106932187A CN 106932187 A CN106932187 A CN 106932187A CN 201710190128 A CN201710190128 A CN 201710190128A CN 106932187 A CN106932187 A CN 106932187A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/10—Determining the moment of inertia
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
- G01M1/122—Determining position of centre of gravity
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The present invention discloses a kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig and test method, belongs to a class undercarriage experimental technique field.The experimental rig includes the Aircraft Quality inertia simulation mechanism that nose-gear, girder steel component, supporting hinges and balancing weight are constituted；Also include the nose-gear load maintainer of hydraulic actuator, tension force pin and pressurized strut hinge composition.The pitch rotation inertia and nose-gear that Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig of the present invention can simulate carrier-borne aircraft shut down load, and by adjusting the influence that the height of C.G. of Aircraft Quality inertia simulation mechanism can be with equivalent carrier-borne aircraft aerodynamic force to nose-gear projection performance.
Description
Technical field：
The present invention relates to a kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig and test method, belong to a class undercarriage
Experimental technique field.
Background technology：
The landing of ship-board aircraft is main with aircraft carrier as base, by the strict limitation of type aircraft carrier deck length, ship-board aircraft
Takeoff distance is very limited, and minimum safe must be reached in extremely short distance from warship speed and corresponding take-off attitude.
Current carrier-borne aircraft takes off two kinds of technological approaches of conventional ski-jump take-off and catapult-assisted take-off, is employed on external advanced aircraft carrier and launched
Fly technology.
When preparing to implement ejection, ejector starts to preload ship-board aircraft, and piston ejector ram, ejector piston is tensioned；When beginning is launched,
Ejector is persistently loaded, and when release load is reached, tension force pin is pulled off, and aircraft is to depart from the constraint for pining down bar, is initially entered
The ejection sliding race stage；At the end of ejection travel, aircraft departs from the constraint of piston ejector ram, ejector piston, enters the free skating of people deck and runs the stage, is pressurized
The nose-gear Quick extension of contracting, aircraft quickly comes back.The quick projection effect of nose-gear makes aircraft be obtained in gunwale
Enough angles of pitch and rate of pitch, and then aircraft is reached the take-off angle of attack as early as possible.Nose-gear projection is that carrier-borne aircraft is used
Front-wheel pulls one of key technology of catapult-assisted take-off.
Projection experiment is the key link for checking Nose Gear Fast-Extension of Carrier Based Aircraft ability, and phase is had no in presently disclosed patent
The technical research of pass.At home in open source literature, Wei little Hui etc. proposes the nose-gear projection experiment side based on equivalent quality
Method, the test method can preferably examine the projection energy of carrier-borne aircraft nose-gear when appropriate equivalent quality coefficient is chosen
Power.But the test method is tested independent undercarriage, do not consider that aerodynamic characteristic and quality of the ship-board aircraft in ejection are used to
Influence of the flow characteristic to nose-gear projection performance.Therefore, prior art need to be improved to solve the deficiency of prior art.
The content of the invention：
The present invention is to provide a kind of Nose Gear Fast-Extension of Carrier Based Aircraft examination to solve the problems, such as above-mentioned prior art
Experiment device and test method, simulation carrier-borne aircraft is in catapult-assisted take-off end nose-gear projection motion process.
The present invention is adopted the following technical scheme that：A kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig, including carrier-borne aircraft quality
Inertia simulation mechanism and nose-gear load maintainer；
The carrier-borne aircraft mass inertia simulation mechanism is made up of girder steel component, nose-gear, supporting hinges and balancing weight,
The nose-gear load maintainer is made up of hydraulic actuator, tension force pin and pressurized strut hinge, and the hydraulic actuator is provided with
Piston rod；
The girder steel component is supported by the supporting hinges for fixing on the ground, is rotated around supporting hinges, the nose-gear
Installed in girder steel component lower section, the nose-gear includes pillar, hound and wheel, and the nose-gear is by pillar and tiltedly
Strut is connected with girder steel component, and as girder steel component is moved together, the balancing weight is arranged on girder steel component, and the hydraulic pressure is made
Dynamic cylinder is vertically installed at nose-gear front, and the hydraulic actuator passes through pressurized strut hinge and the ground for fixing on the ground
Connection, the tension force pin is vertically installed at the top of hydraulic actuator, and tension force pin lower end is connected with the piston rod of hydraulic actuator,
Tension force pin upper end is connected with girder steel component.
The present invention is also adopted the following technical scheme that：A kind of test method of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig, bag
Include following steps：
Step one：Catapult-assisted take-off weight and carrier-borne aircraft aerodynamic characteristics according to carrier-borne aircraft calculate turning for experimental rig
Dynamic inertia and position of centre of gravity, the installation number and installation site for adjusting balancing weight make the rotary inertia of experimental rig and position of centre of gravity
Meet test requirements document；
Step 2：Output loads according to carrier-borne aircraft catapult-assisted take-off end moment ejector calculated and acted on nose-gear
Ejection load vertical component, according to the tension force of the corresponding dialysis load of the ejection load vertical component selection acted on nose-gear
Pin, is connected on hydraulic actuator and girder steel component；
Step 3：The piston-less lumen of hydraulic actuator is connected into oil return, there is rod end chamber to connect hydraulic oil, with hydraulic pressure
Pressurized strut load increases, and girder steel component compresses downwards nose-gear, when hydraulic actuator load increases to tension force pin dialysis pole
In limited time, tension force pin disconnects, and nose-gear drives girder steel component to make projection campaign upwards together.
Further, in step one, the gross weight for adjusting carrier-borne aircraft simulation mechanism is equal with true carrier-borne aircraft take-off weight,
Carrier-borne aircraft simulation mechanism is equal around the rotary inertia of main landing gear wheel shaft with true carrier-borne aircraft around the rotary inertia of supporting hinges；
The center of gravity of carrier-borne aircraft simulation mechanism is as follows with the horizontal range computational methods of supporting hinges：
Wherein：Mg is carrier-borne aircraft gravity, LmIt is the course distance of carrier-borne aircraft center of gravity to main landing gear, q is launched for carrier-borne aircraft
The dynamic pressure of end, S is carrier-borne aircraft wing area of reference, CLIt is lift coefficient, c is mean aerodynamic chord, CmIt is pitching moment system
Number；
Carrier-borne aircraft simulation mechanism center of gravity is as follows with the line of supporting hinges and the angle calcu-lation method of horizontal plane：
Wherein：CLαIt is carrier-borne aircraft lift coefficient to the derivative of the angle of attack, CmαFor carrier-borne aircraft pitching moment coefficient is led to the angle of attack
Number.
The present invention has the advantages that：Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig of the present invention can simulate carrier-borne aircraft
Pitch rotation inertia and nose-gear shut down load, and can by adjusting the height of C.G. of Aircraft Quality inertia simulation mechanism
Influence with equivalent carrier-borne aircraft aerodynamic force to nose-gear projection performance, reduces experimental scale, saves experimentation cost；The experiment
Device is applied to the ejecting type carrier-borne aircraft of different take-off weights, is also applied for the nose-gear of different structure form.
Brief description of the drawings：
Fig. 1 is Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig structure chart.
Wherein：
1st, pressurized strut hinge, 2, hydraulic actuator, 3, tension force pin, 4, nose-gear, 5, balancing weight, 6, girder steel component, 7,
Supporting hinges, 8, pillar, 9, hound, 10, wheel.
Specific embodiment：
The present invention is further illustrated below in conjunction with the accompanying drawings.
Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig of the present invention includes carrier-borne aircraft mass inertia simulation mechanism and nose-gear
Load maintainer, wherein carrier-borne aircraft mass inertia simulation mechanism are by girder steel component 6, nose-gear 4, supporting hinges 7 and balancing weight 5
Constitute；Nose-gear load maintainer is made up of hydraulic actuator 2, tension force pin 3 and pressurized strut hinge 1.
Girder steel component 6 is supported by the supporting hinges 7 for fixing on the ground, can be rotated around supporting hinges 7, simulates carrier-borne aircraft
Elevating movement.Nose-gear 4 is arranged on the lower section of girder steel component 6, and nose-gear 4 includes pillar 8, hound 9 and wheel 10, passes through
The pillar 8 and hound 9 of nose-gear 4 are connected with girder steel component 6, can together be moved with girder steel component 6, nose-gear 4
Wheel 10 it is equal with the distance of supporting hinges 7 and the preceding main wheel track of carrier-borne aircraft.Balancing weight 5 is arranged on girder steel component 6, can be with
The weight of projection experimental rig, position of centre of gravity and rotary inertia are adjusted by the quantity and installation site of balancing weight 5.Hydraulic actuation
Cylinder 2 is vertically installed at the front of nose-gear 4, and the pressurized strut hinge 1 that hydraulic actuator 2 passes through to fix on the ground connects with ground
Connect.Tension force pin 3 is vertically installed at the top of hydraulic actuator 2, and the lower end of tension force pin 3 is connected with the piston rod of hydraulic actuator 2,
The upper end of power pin 3 is connected with girder steel component 6.
The collocation method bag of the carrier-borne aircraft mass inertia simulation mechanism of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig of the present invention
Include：
The gross weight of carrier-borne aircraft simulation mechanism is equal with true carrier-borne aircraft take-off weight, and carrier-borne aircraft simulation mechanism is around bloster hinge
The rotary inertia of chain 7 is equal around the rotary inertia of main landing gear wheel shaft with true carrier-borne aircraft.
The center of gravity of carrier-borne aircraft simulation mechanism is as follows with the horizontal range computational methods of supporting hinges 7：
Wherein：Mg is carrier-borne aircraft gravity, LmIt is the course distance of carrier-borne aircraft center of gravity to main landing gear, q is launched for carrier-borne aircraft
The dynamic pressure of end, S is carrier-borne aircraft wing area of reference, CLIt is lift coefficient, c is mean aerodynamic chord, CmIt is pitching moment system
Number.
Carrier-borne aircraft simulation mechanism center of gravity is as follows with the line of supporting hinges 7 and the angle calcu-lation method of horizontal plane：
Wherein：CLαIt is carrier-borne aircraft lift coefficient to the derivative of the angle of attack, CmαFor carrier-borne aircraft pitching moment coefficient is led to the angle of attack
Number.
The test method of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig of the present invention, step is as follows：
Step one：Catapult-assisted take-off weight and carrier-borne aircraft aerodynamic characteristics according to carrier-borne aircraft calculate turning for experimental rig
Dynamic inertia and position of centre of gravity, adjusting the installation number and installation site of balancing weight 5 makes the rotary inertia of experimental rig and center of gravity position
Put and meet test requirements document；
Step 2：Output loads according to carrier-borne aircraft catapult-assisted take-off end moment ejector calculated and acted on nose-gear
Ejection load vertical component, according to opening for the ejection load vertical component selection correspondence dialysis load acted on nose-gear 4
Power pin 3, is connected on hydraulic actuator 2 and girder steel component 6；
Step 3：The rodless cavity of hydraulic actuator 2 is connected into oil return, rod chamber connects hydraulic oil, as hydraulic actuator 2 is carried
Lotus increases, and girder steel component 6 compresses downwards nose-gear 4, when the load of hydraulic actuator 2 increases to the 3 dialysis limit of tension force pin,
Tension force pin 3 disconnects, and nose-gear 4 drives girder steel component 6 to make projection campaign upwards together.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, some improvement can also be made under the premise without departing from the principles of the invention, these improvement also should be regarded as of the invention
Protection domain.
Claims (3)
1. a kind of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig, it is characterised in that：Including carrier-borne aircraft mass inertia simulation mechanism and
Nose-gear load maintainer；
The carrier-borne aircraft mass inertia simulation mechanism is by girder steel component (6), nose-gear (4), supporting hinges (7) and balancing weight
(5) constitute, the nose-gear load maintainer is made up of hydraulic actuator (2), tension force pin (3) and pressurized strut hinge (1), institute
State hydraulic actuator (2) and be provided with piston rod；
The girder steel component (6) is supported by the supporting hinges (7) for fixing on the ground, is rotated around supporting hinges (7), described preceding
Frame (4) fall installed in girder steel component (6) lower section, the nose-gear (4) includes pillar (8), hound (9) and wheel (10),
The nose-gear (4) is connected by pillar (8) and hound (9) with girder steel component (6), as girder steel component (6) is started shipment
Dynamic, on girder steel component (6), the hydraulic actuator (2) is being vertically installed at nose-gear (4) just to the balancing weight (5)
Front, the hydraulic actuator (2) is connected by the pressurized strut hinge (1) for fixing on the ground with ground, the tension force pin (3)
The top of hydraulic actuator (2) is vertically installed at, tension force pin (3) lower end is connected with the piston rod of hydraulic actuator (2), tension force pin
(3) upper end is connected with girder steel component (6).
2. a kind of test method of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig, it is characterised in that：Comprise the following steps
Step one：The rotation that catapult-assisted take-off weight and carrier-borne aircraft aerodynamic characteristics according to carrier-borne aircraft calculate experimental rig is used to
Amount and position of centre of gravity, the installation number and installation site of adjustment balancing weight (5) make the rotary inertia of experimental rig and position of centre of gravity
Meet test requirements document；
Step 2：Output loads according to carrier-borne aircraft catapult-assisted take-off end moment ejector calculate the bullet acted on nose-gear
Load vertical component is penetrated, according to the tension force of the ejection load vertical component selection correspondence dialysis load acted on nose-gear (4)
Pin (3), is connected on hydraulic actuator (2) and girder steel component (6)；
Step 3：The piston-less lumen of hydraulic actuator (2) is connected into oil return, there is rod end chamber to connect hydraulic oil, with hydraulic pressure
Pressurized strut (2) load increases, and girder steel component (6) compresses downwards nose-gear (4), and when hydraulic actuator (2), load increases to
During tension force pin (3) dialysis limit, tension force pin (3) disconnects, and nose-gear (4) drives girder steel component (6) to make projection fortune upwards together
It is dynamic.
3. the test method of Nose Gear Fast-Extension of Carrier Based Aircraft experimental rig as claimed in claim 2, it is characterised in that：Step one
In, the gross weight for adjusting carrier-borne aircraft simulation mechanism is equal with true carrier-borne aircraft take-off weight, and carrier-borne aircraft simulation mechanism is around bloster hinge
The rotary inertia of chain (7) is equal around the rotary inertia of main landing gear wheel shaft with true carrier-borne aircraft；
The center of gravity of carrier-borne aircraft simulation mechanism is as follows with the horizontal range computational methods of supporting hinges (7)：
Wherein：Mg is carrier-borne aircraft gravity, LmIt is the course distance of carrier-borne aircraft center of gravity to main landing gear, q is carrier-borne aircraft ejection end
Dynamic pressure, S is carrier-borne aircraft wing area of reference, CLIt is lift coefficient, c is mean aerodynamic chord, CmIt is pitching moment coefficient；
Carrier-borne aircraft simulation mechanism center of gravity is as follows with the line of supporting hinges (7) and the angle calcu-lation method of horizontal plane：
Wherein：CLαIt is carrier-borne aircraft lift coefficient to the derivative of the angle of attack, CmαIt is carrier-borne aircraft pitching moment coefficient to the derivative of the angle of attack.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710190128.2A CN106932187B (en) | 2017-03-27 | 2017-03-27 | Device and method for testing protruding of nose landing gear of carrier-based aircraft |
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| CN201710190128.2A CN106932187B (en) | 2017-03-27 | 2017-03-27 | Device and method for testing protruding of nose landing gear of carrier-based aircraft |
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Cited By (7)
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| CN108502207A (en) * | 2018-03-19 | 2018-09-07 | 成都飞机工业（集团）有限责任公司 | Ejection impact ground validation test method |
| CN110501146A (en) * | 2019-07-16 | 2019-11-26 | 中国飞机强度研究所 | Imitative lift simulation and measuring device and measuring method |
| CN113642093A (en) * | 2021-06-01 | 2021-11-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Modeling method for separated ejection type aircraft landing gear |
| CN114379817A (en) * | 2021-12-30 | 2022-04-22 | 中国飞机强度研究所 | Shipboard aircraft nose landing gear catapulting and protruding test device and test method |
| CN116929819A (en) * | 2023-09-18 | 2023-10-24 | 中国飞机强度研究所 | Device and method for testing protrusion of landing gear of carrier-based aircraft |
| CN116946387A (en) * | 2023-09-19 | 2023-10-27 | 中国飞机强度研究所 | Aircraft main landing gear off-ship simulated loading device and simulated loading test method |
| CN116986012A (en) * | 2023-09-25 | 2023-11-03 | 中国飞机强度研究所 | Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108502207A (en) * | 2018-03-19 | 2018-09-07 | 成都飞机工业（集团）有限责任公司 | Ejection impact ground validation test method |
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| CN113642093B (en) * | 2021-06-01 | 2024-05-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Separated ejection type aircraft landing gear modeling method |
| CN113642093A (en) * | 2021-06-01 | 2021-11-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Modeling method for separated ejection type aircraft landing gear |
| CN114379817A (en) * | 2021-12-30 | 2022-04-22 | 中国飞机强度研究所 | Shipboard aircraft nose landing gear catapulting and protruding test device and test method |
| CN114379817B (en) * | 2021-12-30 | 2023-07-21 | 中国飞机强度研究所 | Device and method for catapulting and protruding test of nose landing gear of carrier-based aircraft |
| CN116929819A (en) * | 2023-09-18 | 2023-10-24 | 中国飞机强度研究所 | Device and method for testing protrusion of landing gear of carrier-based aircraft |
| CN116929819B (en) * | 2023-09-18 | 2023-12-12 | 中国飞机强度研究所 | Device and method for testing protrusion of landing gear of carrier-based aircraft |
| CN116946387B (en) * | 2023-09-19 | 2023-12-12 | 中国飞机强度研究所 | Aircraft main landing gear off-ship simulated loading device and simulated loading test method |
| CN116946387A (en) * | 2023-09-19 | 2023-10-27 | 中国飞机强度研究所 | Aircraft main landing gear off-ship simulated loading device and simulated loading test method |
| CN116986012A (en) * | 2023-09-25 | 2023-11-03 | 中国飞机强度研究所 | Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft |
| CN116986012B (en) * | 2023-09-25 | 2023-12-15 | 中国飞机强度研究所 | Device and method for landing gear running obstacle crossing impact test of carrier-based aircraft |
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| CN106932187B (en) | 2023-05-26 |
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